TSAGI 8% AIRFOIL (tsagi8-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: TSAGI 8% AIRFOIL (tsagi8-il) Reynolds number: 100,000 Max Cl/Cd: 44.39 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-tsagi8-il-100000-n5.txt Download as CSV file: xf-tsagi8-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: TSAGI 8% AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5524 0.08882 0.08405 -0.0105 1.0000 0.0225
-8.500 -0.5553 0.08439 0.07968 -0.0133 1.0000 0.0220
-8.250 -0.5619 0.07966 0.07500 -0.0166 1.0000 0.0217
-8.000 -0.5689 0.07531 0.07066 -0.0183 1.0000 0.0213
-7.750 -0.5720 0.07081 0.06614 -0.0200 1.0000 0.0208
-7.500 -0.5738 0.06612 0.06137 -0.0211 1.0000 0.0203
-7.250 -0.5740 0.06131 0.05645 -0.0216 1.0000 0.0200
-7.000 -0.5721 0.05657 0.05154 -0.0215 1.0000 0.0196
-6.750 -0.5681 0.05192 0.04667 -0.0207 1.0000 0.0192
-6.500 -0.5626 0.04734 0.04180 -0.0193 1.0000 0.0190
-6.250 -0.5547 0.04324 0.03737 -0.0176 1.0000 0.0191
-6.000 -0.5448 0.03966 0.03343 -0.0156 1.0000 0.0201
-5.750 -0.5334 0.03622 0.02957 -0.0133 1.0000 0.0210
-5.500 -0.5205 0.03296 0.02584 -0.0108 1.0000 0.0216
-5.250 -0.5057 0.02982 0.02218 -0.0082 1.0000 0.0220
-5.000 -0.4884 0.02703 0.01889 -0.0059 1.0000 0.0226
-4.750 -0.4687 0.02466 0.01601 -0.0039 1.0000 0.0235
-4.500 -0.4471 0.02294 0.01386 -0.0022 1.0000 0.0254
-4.250 -0.4274 0.02125 0.01211 -0.0008 1.0000 0.0287
-4.000 -0.4067 0.01987 0.01058 0.0008 1.0000 0.0315
-3.750 -0.3868 0.01874 0.00929 0.0026 1.0000 0.0362
-3.500 -0.3689 0.01780 0.00835 0.0043 1.0000 0.0432
-3.250 -0.3517 0.01689 0.00740 0.0063 1.0000 0.0531
-3.000 -0.3345 0.01623 0.00672 0.0083 1.0000 0.0686
-2.750 -0.3038 0.01541 0.00600 0.0073 0.9927 0.1036
-2.500 -0.2687 0.01445 0.00538 0.0053 0.9822 0.1844
-2.250 -0.2382 0.01286 0.00497 0.0039 0.9719 0.4592
-2.000 -0.1513 0.01221 0.00564 -0.0048 0.9983 0.9435
-1.750 -0.0860 0.01240 0.00547 -0.0121 1.0000 0.9813
-1.500 -0.0177 0.01229 0.00508 -0.0207 1.0000 1.0000
-1.250 0.0197 0.01219 0.00482 -0.0233 0.9813 1.0000
-1.000 0.0621 0.01212 0.00461 -0.0267 0.9596 1.0000
-0.750 0.1045 0.01204 0.00440 -0.0301 0.9377 1.0000
-0.500 0.1445 0.01196 0.00421 -0.0328 0.9143 1.0000
-0.250 0.1806 0.01190 0.00405 -0.0346 0.8897 1.0000
0.000 0.2120 0.01187 0.00392 -0.0353 0.8653 1.0000
0.250 0.2398 0.01187 0.00383 -0.0352 0.8422 1.0000
0.500 0.2648 0.01190 0.00378 -0.0345 0.8197 1.0000
0.750 0.2893 0.01194 0.00377 -0.0337 0.7994 1.0000
1.000 0.3130 0.01200 0.00378 -0.0328 0.7793 1.0000
1.250 0.3369 0.01207 0.00382 -0.0319 0.7606 1.0000
1.500 0.3609 0.01216 0.00387 -0.0311 0.7426 1.0000
1.750 0.3845 0.01226 0.00399 -0.0302 0.7245 1.0000
2.000 0.4080 0.01237 0.00410 -0.0292 0.7071 1.0000
2.250 0.4313 0.01249 0.00423 -0.0282 0.6900 1.0000
2.500 0.4547 0.01263 0.00439 -0.0272 0.6734 1.0000
2.750 0.4779 0.01278 0.00461 -0.0262 0.6562 1.0000
3.000 0.5010 0.01294 0.00483 -0.0252 0.6384 1.0000
3.250 0.5241 0.01311 0.00507 -0.0241 0.6205 1.0000
3.500 0.5470 0.01329 0.00535 -0.0230 0.6020 1.0000
3.750 0.5699 0.01348 0.00565 -0.0219 0.5815 1.0000
4.000 0.5922 0.01369 0.00593 -0.0206 0.5590 1.0000
4.250 0.6132 0.01388 0.00618 -0.0190 0.5231 1.0000
4.500 0.6303 0.01420 0.00625 -0.0166 0.4474 1.0000
4.750 0.6439 0.01508 0.00650 -0.0141 0.3068 1.0000
5.000 0.6516 0.01729 0.00744 -0.0116 0.0937 1.0000
5.250 0.6662 0.01888 0.00874 -0.0095 0.0450 1.0000
5.500 0.6831 0.02002 0.00992 -0.0077 0.0338 1.0000
5.750 0.6993 0.02122 0.01130 -0.0056 0.0298 1.0000
6.000 0.7155 0.02235 0.01259 -0.0036 0.0261 1.0000
6.250 0.7289 0.02392 0.01418 -0.0014 0.0229 1.0000
6.500 0.7456 0.02544 0.01588 0.0006 0.0217 1.0000
6.750 0.7643 0.02713 0.01773 0.0024 0.0209 1.0000
7.000 0.7842 0.02912 0.01994 0.0041 0.0197 1.0000
7.250 0.8032 0.03106 0.02217 0.0057 0.0181 1.0000
7.500 0.8205 0.03318 0.02458 0.0073 0.0169 1.0000
7.750 0.8357 0.03581 0.02758 0.0093 0.0163 1.0000
8.000 0.8478 0.03869 0.03087 0.0115 0.0161 1.0000
8.250 0.8564 0.04178 0.03438 0.0139 0.0160 1.0000
8.500 0.8611 0.04510 0.03812 0.0164 0.0160 1.0000
8.750 0.8618 0.04856 0.04198 0.0189 0.0161 1.0000
9.000 0.8585 0.05211 0.04588 0.0215 0.0162 1.0000
9.250 0.8507 0.05570 0.04978 0.0238 0.0164 1.0000
9.500 0.8377 0.05923 0.05355 0.0262 0.0165 1.0000
9.750 0.8215 0.06239 0.05687 0.0283 0.0167 1.0000
10.000 0.8033 0.06627 0.06090 0.0285 0.0169 1.0000
10.250 0.7852 0.07089 0.06566 0.0267 0.0170 1.0000
10.500 0.7666 0.07669 0.07156 0.0231 0.0172 1.0000
10.750 0.7482 0.08383 0.07878 0.0180 0.0174 1.0000
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